Optimal excitation mechanism for combustion enhancement of supersonic shear layers with pulsed jets
Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40,...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Liu, Chengcheng [verfasserIn] |
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| Format: |
E-Artikel |
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| Sprache: |
Englisch |
| Erschienen: |
2020transfer abstract |
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| Schlagwörter: |
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| Umfang: |
18 |
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| Übergeordnetes Werk: |
Enthalten in: External auditory canal: Inferior, posterior-inferior, and anterior canal wall overhangs - Dedhia, Kavita ELSEVIER, 2018, official journal of the International Association for Hydrogen Energy, New York, NY [u.a.] |
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| Übergeordnetes Werk: |
volume:45 ; year:2020 ; number:43 ; day:3 ; month:09 ; pages:23674-23691 ; extent:18 |
| Links: |
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| DOI / URN: |
10.1016/j.ijhydene.2020.06.217 |
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ELV051072246 |
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| 245 | 1 | 0 | |a Optimal excitation mechanism for combustion enhancement of supersonic shear layers with pulsed jets |
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| 520 | |a Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. | ||
| 520 | |a Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. | ||
| 650 | 7 | |a Supersonic shear layer |2 Elsevier | |
| 650 | 7 | |a Pulsed jet |2 Elsevier | |
| 650 | 7 | |a Large-scale vortex structure |2 Elsevier | |
| 650 | 7 | |a Limiting formation |2 Elsevier | |
| 650 | 7 | |a Combustion efficiency |2 Elsevier | |
| 700 | 1 | |a Wang, Zi'ang |4 oth | |
| 700 | 1 | |a Yu, Bin |4 oth | |
| 700 | 1 | |a Zhang, Bin |4 oth | |
| 700 | 1 | |a Liu, Hong |4 oth | |
| 773 | 0 | 8 | |i Enthalten in |n Elsevier |a Dedhia, Kavita ELSEVIER |t External auditory canal: Inferior, posterior-inferior, and anterior canal wall overhangs |d 2018 |d official journal of the International Association for Hydrogen Energy |g New York, NY [u.a.] |w (DE-627)ELV000127019 |
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10.1016/j.ijhydene.2020.06.217 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001124.pica (DE-627)ELV051072246 (ELSEVIER)S0360-3199(20)32402-2 DE-627 ger DE-627 rakwb eng 610 VZ 44.94 bkl Liu, Chengcheng verfasserin aut Optimal excitation mechanism for combustion enhancement of supersonic shear layers with pulsed jets 2020transfer abstract 18 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. Supersonic shear layer Elsevier Pulsed jet Elsevier Large-scale vortex structure Elsevier Limiting formation Elsevier Combustion efficiency Elsevier Wang, Zi'ang oth Yu, Bin oth Zhang, Bin oth Liu, Hong oth Enthalten in Elsevier Dedhia, Kavita ELSEVIER External auditory canal: Inferior, posterior-inferior, and anterior canal wall overhangs 2018 official journal of the International Association for Hydrogen Energy New York, NY [u.a.] (DE-627)ELV000127019 volume:45 year:2020 number:43 day:3 month:09 pages:23674-23691 extent:18 https://doi.org/10.1016/j.ijhydene.2020.06.217 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U SSG-OLC-PHA 44.94 Hals-Nasen-Ohrenheilkunde VZ AR 45 2020 43 3 0903 23674-23691 18 |
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10.1016/j.ijhydene.2020.06.217 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001124.pica (DE-627)ELV051072246 (ELSEVIER)S0360-3199(20)32402-2 DE-627 ger DE-627 rakwb eng 610 VZ 44.94 bkl Liu, Chengcheng verfasserin aut Optimal excitation mechanism for combustion enhancement of supersonic shear layers with pulsed jets 2020transfer abstract 18 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. Supersonic shear layer Elsevier Pulsed jet Elsevier Large-scale vortex structure Elsevier Limiting formation Elsevier Combustion efficiency Elsevier Wang, Zi'ang oth Yu, Bin oth Zhang, Bin oth Liu, Hong oth Enthalten in Elsevier Dedhia, Kavita ELSEVIER External auditory canal: Inferior, posterior-inferior, and anterior canal wall overhangs 2018 official journal of the International Association for Hydrogen Energy New York, NY [u.a.] (DE-627)ELV000127019 volume:45 year:2020 number:43 day:3 month:09 pages:23674-23691 extent:18 https://doi.org/10.1016/j.ijhydene.2020.06.217 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U SSG-OLC-PHA 44.94 Hals-Nasen-Ohrenheilkunde VZ AR 45 2020 43 3 0903 23674-23691 18 |
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10.1016/j.ijhydene.2020.06.217 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001124.pica (DE-627)ELV051072246 (ELSEVIER)S0360-3199(20)32402-2 DE-627 ger DE-627 rakwb eng 610 VZ 44.94 bkl Liu, Chengcheng verfasserin aut Optimal excitation mechanism for combustion enhancement of supersonic shear layers with pulsed jets 2020transfer abstract 18 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. Supersonic shear layer Elsevier Pulsed jet Elsevier Large-scale vortex structure Elsevier Limiting formation Elsevier Combustion efficiency Elsevier Wang, Zi'ang oth Yu, Bin oth Zhang, Bin oth Liu, Hong oth Enthalten in Elsevier Dedhia, Kavita ELSEVIER External auditory canal: Inferior, posterior-inferior, and anterior canal wall overhangs 2018 official journal of the International Association for Hydrogen Energy New York, NY [u.a.] (DE-627)ELV000127019 volume:45 year:2020 number:43 day:3 month:09 pages:23674-23691 extent:18 https://doi.org/10.1016/j.ijhydene.2020.06.217 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U SSG-OLC-PHA 44.94 Hals-Nasen-Ohrenheilkunde VZ AR 45 2020 43 3 0903 23674-23691 18 |
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10.1016/j.ijhydene.2020.06.217 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001124.pica (DE-627)ELV051072246 (ELSEVIER)S0360-3199(20)32402-2 DE-627 ger DE-627 rakwb eng 610 VZ 44.94 bkl Liu, Chengcheng verfasserin aut Optimal excitation mechanism for combustion enhancement of supersonic shear layers with pulsed jets 2020transfer abstract 18 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. Supersonic shear layer Elsevier Pulsed jet Elsevier Large-scale vortex structure Elsevier Limiting formation Elsevier Combustion efficiency Elsevier Wang, Zi'ang oth Yu, Bin oth Zhang, Bin oth Liu, Hong oth Enthalten in Elsevier Dedhia, Kavita ELSEVIER External auditory canal: Inferior, posterior-inferior, and anterior canal wall overhangs 2018 official journal of the International Association for Hydrogen Energy New York, NY [u.a.] (DE-627)ELV000127019 volume:45 year:2020 number:43 day:3 month:09 pages:23674-23691 extent:18 https://doi.org/10.1016/j.ijhydene.2020.06.217 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U SSG-OLC-PHA 44.94 Hals-Nasen-Ohrenheilkunde VZ AR 45 2020 43 3 0903 23674-23691 18 |
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10.1016/j.ijhydene.2020.06.217 doi /cbs_pica/cbs_olc/import_discovery/elsevier/einzuspielen/GBV00000000001124.pica (DE-627)ELV051072246 (ELSEVIER)S0360-3199(20)32402-2 DE-627 ger DE-627 rakwb eng 610 VZ 44.94 bkl Liu, Chengcheng verfasserin aut Optimal excitation mechanism for combustion enhancement of supersonic shear layers with pulsed jets 2020transfer abstract 18 nicht spezifiziert zzz rdacontent nicht spezifiziert z rdamedia nicht spezifiziert zu rdacarrier Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. Supersonic shear layer Elsevier Pulsed jet Elsevier Large-scale vortex structure Elsevier Limiting formation Elsevier Combustion efficiency Elsevier Wang, Zi'ang oth Yu, Bin oth Zhang, Bin oth Liu, Hong oth Enthalten in Elsevier Dedhia, Kavita ELSEVIER External auditory canal: Inferior, posterior-inferior, and anterior canal wall overhangs 2018 official journal of the International Association for Hydrogen Energy New York, NY [u.a.] (DE-627)ELV000127019 volume:45 year:2020 number:43 day:3 month:09 pages:23674-23691 extent:18 https://doi.org/10.1016/j.ijhydene.2020.06.217 Volltext GBV_USEFLAG_U GBV_ELV SYSFLAG_U SSG-OLC-PHA 44.94 Hals-Nasen-Ohrenheilkunde VZ AR 45 2020 43 3 0903 23674-23691 18 |
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Enthalten in External auditory canal: Inferior, posterior-inferior, and anterior canal wall overhangs New York, NY [u.a.] volume:45 year:2020 number:43 day:3 month:09 pages:23674-23691 extent:18 |
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optimal excitation mechanism for combustion enhancement of supersonic shear layers with pulsed jets |
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Optimal excitation mechanism for combustion enhancement of supersonic shear layers with pulsed jets |
| abstract |
Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. |
| abstractGer |
Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. |
| abstract_unstemmed |
Supersonic shear layers (convection Mach number = 0.6) with flow direction excitation are studied by a canonical Large Eddy Simulation (LES) method with quasi-laminar turbulent reaction model. By modulating velocity of central jet through ideal square wave under four excitation periods (τ = 20, 40, 60, and 80 μs), the present study aims to explore the optimal excitation mechanism for combustion enhancement. As the excitation period increases, combustion efficiency tends to increase and then decrease. The maximum combustion efficiency is achieved at τ = 40 μ s , which is nearly four times that in the no excitation scenario. The analysis of mixing characteristics of the nonreacting cases reveals that mixing enhancement mainly explains combustion gain of different excitation modes. From the limiting formation of vortex, the size of the vortex core has fully developed to reach axial contact at τ = 40 μ s . Any further increase in excitation intervals implies a larger vortex spacing, which leads to poor fluid mixing while lower excitation case forms continuous small vortices with less mixing region. The comparison of the circulation decomposition of the main vortex and trailing wakes indicates the pinch-off characteristic of the limiting formation of vortical structure. On the basis of these results, an optimal forcing criterion is proposed according to the limiting vortex formation with dimensionless excitation time scale τ ∗ ≈ 1.64 . This study provides a novel perspective for the optimal combustion enhancement of supersonic shear layers from the aspect of vorticity dynamics. |
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Optimal excitation mechanism for combustion enhancement of supersonic shear layers with pulsed jets |
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